CN114749667B - Manufacturing method of helicopter rotor blade balance weight alloy - Google Patents
Manufacturing method of helicopter rotor blade balance weight alloy Download PDFInfo
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- CN114749667B CN114749667B CN202210245435.7A CN202210245435A CN114749667B CN 114749667 B CN114749667 B CN 114749667B CN 202210245435 A CN202210245435 A CN 202210245435A CN 114749667 B CN114749667 B CN 114749667B
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- balance weight
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- alloy solder
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
- B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Powder Metallurgy (AREA)
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Abstract
The invention relates to the technical field of helicopter rotors, in particular to a method for manufacturing a helicopter rotor blade balance weight alloy, which comprises the following steps of Sp1: preparing a brass alloy sheet according to the required material amount, and smelting and atomizing the brass alloy sheet by a vacuum furnace to prepare injection molding powder, sp2: feeding injection molding powder into an injection molding machine, and cooling and molding to obtain a regenerated blank, sp3: the method comprises the steps of degreasing, proportioning and regenerating the blank, sintering the degreased blank, annealing the sintered blank to obtain the blank, and pre-calculating a required density value of the alloy solder according to the actual weight, wherein the balance weight with the required weight characteristic is manufactured by selecting the alloy solder according to the density value, the weight of the balance weight can be adjusted without mechanically improving the volume of a casting mould, the mechanical modification of the casting mould is avoided, the weight adjustment mode of the balance weight is optimized, and the weight adjustment cost of the balance weight is reduced.
Description
Technical Field
The invention relates to the technical field of helicopter rotors, in particular to a method for manufacturing a balance weight alloy of a helicopter rotor blade.
Background
Helicopter rotor is used as an important component of a helicopter, provides required lift force and propulsion force for the flight of the helicopter, is a main vibration source of the helicopter, and is a common cause for the mass unbalance and aerodynamic unbalance of the helicopter rotor blade to aggravate the vibration of a machine body, and a balance weight is used in the design of the helicopter rotor blade in order to realize the static balance of the blade.
In the process of manufacturing the balance weight, the weight of the balance weight is often required to be adjusted, the mechanical structure of the casting mold is required to be modified, the volume of the casting mold is required to be increased or reduced by a small part, the modification is energy-consuming and time-consuming, and the weight adjustment cost of the balance weight is high. In view of this, we propose a method of manufacturing a helicopter rotor blade balance weight alloy.
Disclosure of Invention
The invention aims to provide a manufacturing method of a balancing weight alloy of a helicopter rotor blade, which aims to solve the problems that in the background art, the weight of the balancing weight is required to be regulated in the process of manufacturing the balancing weight, the weight regulation needs to be mechanically structurally modified on a casting mould, the volume of the casting mould is required to be increased or reduced by a small part, the modification is energy-consuming and time-consuming, and the weight regulation cost of the balancing weight is high.
In order to achieve the above purpose, the present invention provides the following technical solutions:
a method of making a helicopter rotor blade balance weight alloy comprising the steps of:
sp1: preparing a brass alloy sheet according to the required material amount, and smelting and atomizing the brass alloy sheet by a vacuum furnace to prepare injection molding powder;
sp2: feeding injection molding powder into an injection molding machine, and cooling and molding to obtain a balance weight blank;
sp3: degreasing the balance weight blank, sintering the degreased balance weight blank, and annealing the sintered balance weight blank to obtain a balance weight blank;
sp4: according to the actual weight requirement of the balance weight, calculating a required density value of the alloy solder through a required density proportion formula of the alloy solder, and selecting the alloy solder corresponding to the required density value according to the required density value;
sp5: tin plating is carried out on the edge of the balance weight blank, and then an alloy solder layer is coated by using a soldering iron to prepare the balance weight.
Preferably, the density ratio formula of the alloy solder is specifically as follows:
ρ（a）=ρ（b）×（1-c）
wherein: ρ (a) is a desired density value of the alloy solder, ρ (b) is an original density value of the alloy solder, and c is an adjustment ratio difference.
Preferably, the calculation formula of the adjustment ratio difference value is specifically:
c=（d（e）-d（f））/ d（f）
wherein: d (e) is the original weight value of the alloy solder, and d (f) is the required weight value of the alloy solder.
Preferably, the alloy solder is a component made of tin, copper, zinc, aluminum and silver.
Preferably, the alloy solder has a melting point of 160-280 ℃.
Preferably, the smelting temperature of the brass alloy sheet is 1200-1280 ℃.
Preferably, the specific degreasing treatment mode is to add nitric acid and charge nitrogen gas when the temperature is raised to 90-130 ℃, and the degreasing time is 3-4 h.
Preferably, the specific treatment mode of sintering is to heat the material to 700-1200 ℃ for 2-4 h.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, the required density value of the alloy solder can be calculated in advance according to the actual weight preparation requirement, the balance weight with the required weight characteristic can be manufactured by selecting the alloy solder according to the density value, the weight of the balance weight can be adjusted without mechanically improving the shape volume of the casting mold, the mechanical transformation of the casting mold is avoided, the weight adjustment mode of the balance weight is optimized, and the weight adjustment cost of the balance weight is reduced.
Drawings
FIG. 1 is a flow diagram of a method of manufacturing a helicopter rotor blade balance weight alloy.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1, the present invention provides a technical solution:
a method of making a helicopter rotor blade balance weight alloy comprising the steps of:
sp1: preparing a brass alloy sheet according to the required material amount, and smelting and atomizing the brass alloy sheet by a vacuum furnace to prepare injection molding powder;
sp2: feeding injection molding powder into an injection molding machine, and cooling and molding to obtain a balance weight blank;
sp3: degreasing the balance weight blank, sintering the degreased balance weight blank, and annealing the sintered balance weight blank to obtain a balance weight blank;
sp4: according to the actual weight requirement of the counterweight, calculating a required density value of the alloy solder through a required density proportion formula of the alloy solder, and selecting the alloy solder corresponding to the required density value according to the required density value;
sp5: tin plating is carried out on the edge of the balance weight blank, and then an alloy solder layer is coated by using a soldering iron to prepare the balance weight.
As a preferred implementation manner in this example, the density ratio formula required by the alloy solder is specifically:
ρ（a）=ρ（b）×（1-c）
wherein: ρ (a) is a desired density value of the alloy solder, ρ (b) is an original density value of the alloy solder, and c is an adjustment ratio difference.
The calculation formula of the adjustment ratio difference value is specifically as follows:
c=（d（e）-d（f））/ d（f）
wherein: d (e) is the original weight value of the alloy solder, and d (f) is the required weight value of the alloy solder.
If it is known that the required weight value of the alloy solder is 27.12g, the raw weight value of the alloy solder is 26g, and the raw density value of the alloy solder is 9300 kg/m3, the adjustment ratio difference is 0.043, and the required density value of the alloy solder is 8900.1 kg/m3.
As a preferred embodiment of the present embodiment, the alloy solder is a member made of tin, copper, zinc, aluminum, and silver.
As a preferred embodiment in this example, the alloy solder has a melting point of 160 ℃.
As a preferred embodiment in this example, the melting temperature of the brass alloy sheet was 1200 ℃.
As a preferred implementation manner in the embodiment, the degreasing is specifically performed by heating to 90 ℃, adding nitric acid and charging nitrogen, and degreasing for 3 hours.
As a preferred embodiment in this example, the specific treatment mode of sintering is to raise the temperature to 700 ℃ and keep the temperature for 2 hours.
In summary, according to the invention, the required density value of the alloy solder can be calculated in advance according to the actual weight preparation requirement and the required weight characteristic balance weight can be manufactured by selecting the alloy solder according to the density value, the weight of the balance weight can be adjusted without mechanically improving the shape and the volume of the casting mold, the mechanical transformation of the casting mold is avoided, the weight adjustment mode of the balance weight is optimized, and the weight adjustment cost of the balance weight is reduced.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above-described embodiments, and that the above-described embodiments and descriptions are only preferred embodiments of the present invention, and are not intended to limit the invention, and that various changes and modifications may be made therein without departing from the spirit and scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. A manufacturing method of a helicopter rotor blade balance weight alloy is characterized in that: the method comprises the following steps:
sp1: preparing a brass alloy sheet according to the required material amount, and smelting and atomizing the brass alloy sheet by a vacuum furnace to prepare injection molding powder;
sp2: feeding injection molding powder into an injection molding machine, and cooling and molding to obtain a balance weight blank;
sp3: degreasing the balance weight blank, sintering the degreased balance weight blank, and annealing the sintered balance weight blank to obtain a balance weight blank;
sp4: according to the actual weight requirement of the balance weight, calculating a required density value of the alloy solder through a required density proportion formula of the alloy solder, and selecting the alloy solder corresponding to the required density value according to the required density value;
the density proportion formula required by the alloy solder is specifically as follows:
ρ（a）=ρ（b）×（1-c）
wherein: ρ (a) is the required density value of the alloy solder, ρ (b) is the original density value of the alloy solder, and c is the adjustment ratio difference;
the calculation formula of the adjustment proportion difference value is specifically as follows:
c=（d（e）-d（f））/ d（f）
wherein: d (e) is the original weight value of the alloy solder, and d (f) is the required weight value of the alloy solder;
sp5: tin plating is carried out on the edge of the balance weight blank, and then an alloy solder layer is coated by using a soldering iron to prepare the balance weight.
2. The method of manufacturing a helicopter rotor blade balance weight alloy of claim 1 wherein: the alloy solder is a component made of tin, copper, zinc, aluminum and silver.
3. The method of manufacturing a helicopter rotor blade balance weight alloy of claim 1 wherein: the melting point of the alloy solder is 160-280 ℃.
4. The method of manufacturing a helicopter rotor blade balance weight alloy of claim 1 wherein: the smelting temperature of the brass alloy sheet is 1200-1280 ℃.
5. The method of manufacturing a helicopter rotor blade balance weight alloy of claim 1 wherein: the specific degreasing treatment mode is to add nitric acid and charge nitrogen when the temperature is raised to 90-130 ℃, and the degreasing time is 3-4 h.
6. The method of manufacturing a helicopter rotor blade balance weight alloy of claim 1 wherein: the specific treatment mode of sintering is to heat the material to 700-1200 deg.c for 2-4 hr.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210245435.7A CN114749667B (en) | 2022-03-14 | 2022-03-14 | Manufacturing method of helicopter rotor blade balance weight alloy |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210245435.7A CN114749667B (en) | 2022-03-14 | 2022-03-14 | Manufacturing method of helicopter rotor blade balance weight alloy |
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| CN114749667A CN114749667A (en) | 2022-07-15 |
| CN114749667B true CN114749667B (en) | 2023-07-21 |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0354666A1 (en) * | 1988-07-13 | 1990-02-14 | Kawasaki Steel Corporation | Alloy steel powders for injection molding use, their commpounds and a method for making sintered parts from the same |
| JP2001050350A (en) * | 1999-08-10 | 2001-02-23 | Nkk Seimitsu Kk | Balance weight |
| JP2012241679A (en) * | 2011-05-24 | 2012-12-10 | Horiko Seisakusho:Kk | Weight adjusting method for blade and blade using the method |
| CN104439259A (en) * | 2014-11-25 | 2015-03-25 | 北京康普锡威科技有限公司 | Preparation method of short-process spherical passivated alloy welding powder |
| CN105251992A (en) * | 2015-11-25 | 2016-01-20 | 宁波渝鑫金属粉末科技有限公司 | Preparation method of alloy counterweight block injected and molded by powder |
| CN105644773A (en) * | 2014-11-15 | 2016-06-08 | 徐文进 | Tungsten alloy aircraft counterweight balance weight and manufacturing process thereof |
| CN107855533A (en) * | 2017-11-16 | 2018-03-30 | 北京科技大学 | A kind of method that combination injection molding technology prepares diamond/copper composite |
| CN108380869A (en) * | 2018-03-15 | 2018-08-10 | 东莞华晶粉末冶金有限公司 | Inexpensive 310 powder of stainless steel injection moulding cerul feeding and preparation method thereof |
| CN209800620U (en) * | 2019-02-21 | 2019-12-17 | 昆山嘉升精密电子工业有限公司 | Combined type balancing weight |
| CN112570710A (en) * | 2020-12-31 | 2021-03-30 | 江苏米莫金属股份有限公司 | Tungsten alloy powder casting processing method |
| CN213354821U (en) * | 2020-10-10 | 2021-06-04 | 江西洪都航空工业集团有限责任公司 | Built-in detachable aircraft control surface counterweight structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8007373B2 (en) * | 2009-05-19 | 2011-08-30 | Cobra Golf, Inc. | Method of making golf clubs |
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2022
- 2022-03-14 CN CN202210245435.7A patent/CN114749667B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0354666A1 (en) * | 1988-07-13 | 1990-02-14 | Kawasaki Steel Corporation | Alloy steel powders for injection molding use, their commpounds and a method for making sintered parts from the same |
| JP2001050350A (en) * | 1999-08-10 | 2001-02-23 | Nkk Seimitsu Kk | Balance weight |
| JP2012241679A (en) * | 2011-05-24 | 2012-12-10 | Horiko Seisakusho:Kk | Weight adjusting method for blade and blade using the method |
| CN105644773A (en) * | 2014-11-15 | 2016-06-08 | 徐文进 | Tungsten alloy aircraft counterweight balance weight and manufacturing process thereof |
| CN104439259A (en) * | 2014-11-25 | 2015-03-25 | 北京康普锡威科技有限公司 | Preparation method of short-process spherical passivated alloy welding powder |
| CN105251992A (en) * | 2015-11-25 | 2016-01-20 | 宁波渝鑫金属粉末科技有限公司 | Preparation method of alloy counterweight block injected and molded by powder |
| CN107855533A (en) * | 2017-11-16 | 2018-03-30 | 北京科技大学 | A kind of method that combination injection molding technology prepares diamond/copper composite |
| CN108380869A (en) * | 2018-03-15 | 2018-08-10 | 东莞华晶粉末冶金有限公司 | Inexpensive 310 powder of stainless steel injection moulding cerul feeding and preparation method thereof |
| CN209800620U (en) * | 2019-02-21 | 2019-12-17 | 昆山嘉升精密电子工业有限公司 | Combined type balancing weight |
| CN213354821U (en) * | 2020-10-10 | 2021-06-04 | 江西洪都航空工业集团有限责任公司 | Built-in detachable aircraft control surface counterweight structure |
| CN112570710A (en) * | 2020-12-31 | 2021-03-30 | 江苏米莫金属股份有限公司 | Tungsten alloy powder casting processing method |
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| CN114749667A (en) | 2022-07-15 |
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